2個のホイールによる人工衛星のフィードバック姿勢制御

抄録

The feedback control of attitude changes for a spacecraft with two reaction wheels is considered. Rodriguez parameters are used for attitude expression, and the system is expressed in a simple non-holonomic form. Then a continuous feedback law is proposed for the three-axis control of spacecraft attitude. The stability of the closed-loop system is examined by an equivalent linearized system. The validity of the control law is verified by numerical simulations.